The determination of the natural frequencies and normal modes of vibration for continuous panels, representing more or less typical fuselage skin-panel construction for modern airplanes, is discussed in this paper. The time-dependent boundary conditions at the supporting stringers are considered. A numerical example is presented, and analytical results for a particular structural configuration agree favorably with available experimental measurements.
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Free Vibration of Continuous Skin-Stringer Panels
Y. K. Lin
University of Illinois, Urbana, Ill.
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Lin, Y. K. (December 1, 1960). "Free Vibration of Continuous Skin-Stringer Panels." ASME. J. Appl. Mech. December 1960; 27(4): 669–676. https://doi.org/10.1115/1.3644080
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